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Parametric analysis of composite sinusoidal specimens under quasi-static crushing

Published online by Cambridge University Press:  04 June 2018

H. L. Mou ,
X. Su ,
J. Xie  and
Z. Y. Feng
H. L. Mou
Affiliation:
Key Laboratory of Civil Aircraft Airworthiness TechnologyCivil Aviation University of ChinaTianjinChinacaucstructure@163.com
X. Su
Affiliation:
Key Laboratory of Civil Aircraft Airworthiness TechnologyCivil Aviation University of ChinaTianjinChinacaucstructure@163.com
J. Xie
Affiliation:
Key Laboratory of Civil Aircraft Airworthiness TechnologyCivil Aviation University of ChinaTianjinChinacaucstructure@163.com
Z. Y. Feng
Affiliation:
Key Laboratory of Civil Aircraft Airworthiness TechnologyCivil Aviation University of ChinaTianjinChinacaucstructure@163.com
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Abstract

This paper aims to build the finite element model of the composite sinusoidal specimens and to carry out the parametric analysis. In this paper, the damage behaviour and the energy-absorbing results of composite sinusoidal specimens have been studied by quasi-static crushing experiments. The failure mechanisms of specimens under quasi-static crushing is further analysed. A numerical simulation has been performed by using the finite element model code LS-DYNA. The numerical results, in terms of load -displacement data, have been compared against experimental data, and good agreement has been found. Moreover, a sensitivity study has been carried out by varying material properties in order to assess their influence on the numerical results, and the material parameter selection scheme is optimised based on the constructed corresponding response surfaces. The results show that the response surface model has passed the test of goodness of fit, and the optimisation method can effectively assist the finite element modelling, and greatly decrease the numbers of trial and error.

Keywords

Composite sinusoidal specimenenergy-absorbing characteristicsfailure modefinite element modeloptimisation method
Type
Research Article
Information
The Aeronautical Journal , Volume 122 , Issue 1254 , August 2018 , pp. 1244 - 1262
Copyright
Copyright © Royal Aeronautical Society 2018 

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